CROSS REFERENCE TO RELATED APPLICATIONS
TECHNICAL FIELD
[0002] The present invention generally relates to vehicle systems, and more particularly,
but not exclusively, to airborne thermal and power systems.
BACKGROUND
[0003] Providing thermal and/or power systems to payloads aboard vehicles such as aircraft
remains an area of interest. Some existing systems have various shortcomings relative
to certain applications. Accordingly, there remains a need for further contributions
in this area of technology.
SUMMARY
[0004] One embodiment of the present invention is a unique system for delivering power and/or
thermal conditioning services. Other embodiments include apparatuses, systems, devices,
hardware, methods, and combinations for powering and cooling a payload aboard an aircraft.
Further embodiments, forms, features, aspects, benefits, and advantages of the present
application shall become apparent from the description and figures provided herewith.
BRIEF DESCRIPTION OF THE FIGURES
[0005]
Figure 1 depicts one embodiment of the instant application.
Figure 2 depicts an embodiment of a gas turbine engine.
Figure 3 depicts one embodiment of the instant application.
Fig. 4 depicts an embodiment of the instant application.
Fig. 5 depicts an embodiment of the instant application.
DETAILED DESCRIPTION OF THE ILLUSTRATIVE EMBODIMENTS
[0006] For the purposes of promoting an understanding of the principles of the invention,
reference will now be made to the embodiments illustrated in the drawings and specific
language will be used to describe the same. It will nevertheless be understood that
no limitation of the scope of the invention is thereby intended. Any alterations and
further modifications in the described embodiments, and any further applications of
the principles of the invention as described herein are contemplated as would normally
occur to one skilled in the art to which the invention relates.
[0007] With reference to Fig. 1, an aircraft 50 is depicted having an engine 52 used to
propel the aircraft 50. The aircraft 50 can be operated at a variety of altitudes
and airspeeds and can take a variety of forms. As will be described further below,
the aircraft 50 includes a payload 54 that can be powered by a work providing device
56. As used herein, the term "aircraft" includes, but is not limited to, helicopters,
airplanes, unmanned space vehicles, fixed wing vehicles, variable wing vehicles, rotary
wing vehicles, unmanned combat aerial vehicles, tailless aircraft, hover crafts, and
other airborne and/or extraterrestrial (spacecraft) vehicles. Further, the present
inventions are contemplated for utilization in other applications that may not be
coupled with an aircraft such as, for example, naval vessels, security systems, perimeter
defense/security systems, and the like known to one of ordinary skill in the art.
[0008] Though the aircraft 50 is depicted as having a single engine 52 in the illustrated
embodiment, in some forms the aircraft 50 can have multiple engines. Whether having
a single or multiple engines, any given engine 52 in any given application can take
a variety of forms such as reciprocating engines and gas turbine engines. In one non-limiting
application the engine(s) 52 can be AE 2100 engines provided by the Rolls-Royce Corporation
located at 2100 South Tibbs Avenue, Indianapolis, IN. The engine(s) 52 can be capable
of powering useful devices aboard the aircraft 50, such as, but not limited to, cockpit
lights, instruments, navigational aids and communication devices, to set forth just
a few non-limiting examples. The engine(s) 52 can, but need not, be used to power
a generator and provide environmental control aboard the aircraft 50.
[0009] In one embodiment the work providing device 56 can take the form of an ancillary
engine which can take on a variety of forms capable of producing work that can be
used to operate other devices. The ancillary engine 56 can be an internal combustion
engine which can take on a variety of forms including, but not limited to, a turbine
engine. In one particular non-limiting embodiment the ancillary engine 56 is a gas
turbine engine. To illustrate just one non-limiting example, the ancillary engine
56 can be a M250 engine, or modified version thereof, provided by the Rolls-Royce
Corporation located at 2100 South Tibbs Avenue, Indianapolis, IN. For ease of description
below, the work providing device 56 may alternately be an ancillary engine 56, and
in some cases a gas turbine engine 56, but no limitation as to the work providing
device 56 is intended. The ancillary engine 56 can be a non-propulsive engine in that
the engine 56 can provide an insignificant amount of forward power, such as thrust,
to the vehicle owing to the location, pressure, and flow rate of its exhaust. Such
thrust as might be had from the exhaust can be much less than the thrust provided
from the engine(s) 52.
[0010] In one embodiment the internal combustion engine 56 can be a production engine that
is nominally used to produce a motive force for an aircraft but otherwise modified
for purposes of the instant application to act in a substantially non-propulsive capacity.
Such a motive force for the production engine might have taken the form of a thrust,
such as for example through a propeller in a turboprop engine or a helicopter rotor
of a turboshaft, to set forth just two non-limiting examples. The engine might have
also provided a thrust through a jet action. To set forth just two non-limiting examples
of a production engine, the engine could be an existing helicopter or turboshaft power
plant used in civilian or military applications. The internal combustion engine could
also be a variant of a production engine. In one non-limiting embodiment of the variant,
the internal combustion engine can be a core from a production engine used to provide
a motive thrust for an aircraft, but otherwise modified to be used as a power source
having uses described herein. For example, a high pressure compressor, turbine, and
combustor can be used from an existing engine and modified for purposes of using the
engine as the internal combustion engine described herein.
[0011] The ancillary engine 56 can be a gas turbine engine, an embodiment of which is shown
in Fig. 2. The gas turbine engine can be capable of combusting a mixture of compressed
air and fuel and extracting a power to be provided to useful components aboard the
aircraft 50, whether that power is mechanical, electrical, or otherwise. In one form
the gas turbine engine 56 can include a compressor 58, combustor 60, and turbine 62.
Though depicted as a single spool engine, the gas turbine engine 56 can include greater
numbers of components such as the compressor and turbine and can additionally include
an additional spool(s).
[0012] The ancillary engine 56 can be used to provide power to the payload 54. In one embodiment
the payload 54 receives electrical power from the ancillary engine 56. In one non-limiting
form, the payload receives power from the ancillary engine 56 through a generator
(not shown) that is powered by the ancillary engine 56. Such a generator, and/or associated
electronics, can provide electrical power to the payload at a variety of power levels.
The payload 54, furthermore, can be capable of receiving AC or DC power. In some forms
the payload 54 can have associated electronics to convert, condition, or modify the
power received from the generator into a power useful to its system.
[0013] In one form the payload 54 can be an energy device capable of producing a directional
electromagnetic beam. In some forms the payload 54 can be a directed energy weapon.
The weapon system can take the form of a high power microwave, or a high power laser
based weapon system, to set forth just two non-limiting examples. The weapon system
can be capable of being selectively employed during portions of the operation of the
aircraft 50. In certain embodiments, some portions of the weapon system can be powered
while others are not. In some applications the weapon system can be powered substantially
during the entire operation of the aircraft, while in other applications the weapon
system is substantially non-active to set forth just two non-limiting examples.
[0014] Turning now to Fig. 3, an embodiment of the aircraft 50 is shown having the work
providing device 56 located in a pod 64. The pod 64 of the illustrated embodiment
is coupled to the aircraft 50 and can be located in some embodiments such that it
projects into a free stream. The pod 64 can be releasably coupled to the aircraft
50 or can be permanently affixed thereto. In one form the pod 64 includes a shape
similar to an external fuel tank. The pod 64 can be located beneath a wing or a centerline
of an aircraft, among other possible locations. The pod 64 can have a leading edge
and a trailing edge and in one form has a symmetric shape about one or more axes or
planes. In other embodiments the pod 64 need not be symmetric. The pod 64 can take
a variety of forms and need not be entirely exposed to the free stream such as an
external fuel tank is exposed. In some embodiments the pod 64 can take the form of
a conformal fuel tank used on some types of aircraft to increase a load carrying capacity.
Such a conformal structure need not be exposed to the free stream as some external
fuel tanks are exposed.
[0015] Fig. 4 depicts one embodiment of a thermal conditioning system 66 used in conjunction
with the work providing device 56 located in the pod 64. As will be discussed further
below, the work providing device 56 is used to provide power to the payload 54 (not
shown) in the aircraft 50, as well as to provide power to the thermal conditioning
system 66 which can be used to exchange heat with the payload 54. The pod 64 is depicted
as including a gas turbine engine 56 configured to receive a fuel from the aircraft
50 via fuel passage 67. The fuel can be taken from a fuel reservoir used to provide
fuel to the engines 52, but in other embodiments the fuel can originate from a separate
reservoir. In other additional and/or alternative embodiments, the gas turbine engine
56 can be configured to receive a fuel from a reservoir located within the pod 64.
Such a reservoir can be supplied fuel from the aircraft and/or can be separate from
any aircraft fuel systems.
[0016] In the illustrated embodiment the engine 56 is provided bleed air from one or more
engines 52 via a passage 68. In other additional and/or alternative embodiments the
engine 56 can receive air from sources other than the bleed air depicted in the illustrated
embodiment. The engine(s) 52 can be configured to provide bleed air for additional
purposes other than to provide engine 56 with a source of air for its working cycle.
Furthermore, the bleed air provided to the engine 56 can be modulated at a variety
of locations between the engine(s) 52 and engine 56.
[0017] The engine 56 of Fig. 4 is structured to provide mechanical power to a power generation
device 70 that, in one form, is a high speed generator. The power generation device
70 can take any variety of forms suitable for producing power derived from the engine
56 and can include power control electronics. One or more devices of the electrical,
mechanical, and/or electromechanical kind can be used to provide for generation of
electrical power. For example, any variety of gears, shafts, gear boxes, clutches,
etc can be coupled between the engine 56 and the power generation device 70.
[0018] The thermal conditioning system 66 is operated using power from the engine 56, and
in the illustrated embodiment is operated using power supplied by an intermediate
power generation device 70. The thermal conditioning system 66 is depicted as a refrigerant
cycle system having a refrigerant compressor 72, condenser 74, receiver/circulation
pump 76, an evaporator (not shown), and a thermal energy storage device 78. Though
the illustrated embodiment depicts devices useful to operate a cyclic refrigerant
cycle thermal system, other types of thermal conditioning systems are contemplated
herein. Furthermore, though a cyclic refrigeration cycle is used in combination with
the thermal energy storage device 78, other devices capable of exchanging heat with
the thermal energy storage device 78 are contemplated herein.
[0019] The thermal energy storage device 78 can be located in a fuselage of the aircraft
50, but other locations are also contemplated herein. In addition, the thermal energy
storage device 78 can take the form of any device useful for storing and/or releasing
energy. For example, in one non-limiting form the thermal energy storage device 78
can take the form of a phase change material capable of being placed in one phase
and either releasing or absorbing heat to be placed into another phase. In one non-limiting
example, a phase change material of the thermal energy storage device 78 can be used
to absorb heat from the payload 54 and thereby change phase from a solid to a liquid
and/or vapor. In another non-limiting example the phase change material could change
from a liquid to a vapor. Once thermal energy storage device 78 has received an amount
of thermal energy the thermal conditioning system 66 can be used to change the phase
of the phase change material from a vapor to either a liquid or solid, or from a liquid
to a solid. For example, a working fluid of the thermal conditioning system 66 after
it has pass through an evaporator can be in thermal communication with the thermal
energy storage device 78 to provide cooling. Any type of heat transfer mechanism is
contemplated herein. The thermal energy storage device 78 in turn can be located in
proximity to the payload 54 or can be in thermal communication with the payload 54
such as, for example, through conductivity to set for just one non-limiting possibility.
In this way heat from the payload 54 is transferred to the thermal conditioning system
66 via the thermal energy storage device 78.
[0020] In one non-limiting example of operating the thermal energy storage device 78, if
the payload 54 is operated in a way that increases its temperature, such as by operating
a directed energy weapon 54, then the thermal energy storage device 78 can be used
to absorb heat to maintain system temperatures within an acceptable level of the payload
54. The thermal energy storage device 78 can absorb heat and transfer the heat through
cooling action of the thermal conditioning system 66. In one form a phase change material
of the thermal energy storage device 78 absorbs sufficient heat to transition to a
liquid. The thermal conditioning system 66 can be used to return the phase change
material to a solid state ready to absorb heat upon another operation of the payload
54.
[0021] Though the power generation device 70 is shown in closer proximity to the refrigerant
compressor 72 in the illustrated embodiment, it will be appreciated that the illustrated
embodiment is only an example and other locations and arrangements are contemplated
herein. Furthermore, though the compressor 72 is shown as capable of receiving electrical
power from the power generation device 70, in some forms the compressor 72 can receive
mechanical power from the work providing device 56. For example, in some embodiments
the performance/operability of the compressor 72 can be dependent upon mechanical
shaft speed, while in other embodiments the performance/operability can be independent
on shaft speed when sufficient electrical power is generated by the power generation
device 70. It will be appreciated that any variety of variations of mechanically driven
compressor 72, electrically driven compressor 72 are contemplated herein.
[0022] The power generation device 70 is shown located in the fuselage and can provide power
to the payload 54 as shown in the illustrated embodiment via power transmission 80.
Locations other than the fuselage are also contemplated herein. The power generation
device 70 can provide power to the payload 54 during operation of the aircraft 50.
In some embodiments the power generation device 70 can be used to provide intermittent
power to the payload 54.
[0023] The pod 64 in the illustrated embodiment also has provisions to receive power from
the aircraft 50, via power transmission 82, to power one or more devices within the
pod 64. In one non-limiting embodiment the power transmission 82 can provide power
to controllers and/or auxiliaries located within the pod 64. In one form the power
transmission 82 provides power to supervisory and/or local controls 84 within the
pod 64. In some forms the devices can be located aboard the aircraft 50 and other
transmission mechanisms can be used to convey information/power to systems within
the pod 64.
[0024] Also illustrated in Fig. 4 is a DC/DC converter 86 useful for converting voltage
delivered from the work providing device 56 to an acceptable voltage for use with
the payload 54. Many different types of electrical components can be used to transition
power from the work providing device 56 to the payload 54. For example, in one non-limiting
embodiment an AC/DC converter can be used to convert from an a/c power provided by
the power generation device 70 to the payload 54.
[0025] The dashed lines in the lower right hand corner of Fig. 4 indicates that in an embodiment
having two pods, the airframe fuselage DC/DC converter and thermal energy storage
system can be served by devices in the other pod.
[0026] Turning now to Fig. 5, one embodiment illustrates the aircraft 50 including two separate
pods 64, each capable of providing power and thermal conditioning to the payload 54.
Though two pods 64 are illustrated in Fig. 5, it will be appreciated that other embodiments
can include any number of pods. The payload 54 can include a directed energy device
88, such as a laser, which can be in thermal communication with the thermal energy
storage device 78. The thermal energy storage device 78 is in thermal communication
with the directed energy device 88 via a fluid that circulates by a pump 90. The fluid
can be cooled by thermal energy storage device 78 and heated by the directed energy
device 88.
[0027] As illustrated, each of the pods 64 are configured to receive bleed air, fuel, and
electrical power from the aircraft 50. The pods are also configured to convey a working
fluid, such as a refrigerant, from the thermal conditioning system 66 to the thermal
energy storage device 78. The pods 64 are also configured to deliver power and/or
accept power to the directed energy member 88. In one non-limiting form the directed
energy member 88 provides electrical power to a converter 86 which supplies the power
to the directed energy member 88.
[0028] In some forms of the instant application the work providing device 56 can be quickly
coupled and decoupled from the aircraft 50. In additional and/or alternative forms
the work providing device 56 can be coupled to one of the pod 64, payload 54, bus
80, or thermal conditioning system 66 at the same time that the pod 64 is attached
or removed from the aircraft 50. In other forms the working producing device 56 can
be attached to the aircraft 50 while in the pod 64 and then coupled with an installed
one or more of the payload 54, bus 80, or thermal conditioning system 66.
[0029] One aspect of the present application provides an apparatus comprising vehicle having
an internal combustion engine for providing motive force to enable movement of the
vehicle, a work providing device apart from the internal combustion engine and structured
to generate electrical power by a change in pressure of a fluid, a thermal conditioning
system powered by the work providing device and having a working fluid and a phase
transition material capable of transferring heat with a vehicle component, the working
fluid capable of cooling the phase transition material to cause a change in phase
of the phase transition material, and an electrically driven device disposed in the
vehicle and configured to receive power from the work providing device, the electrically
driven device having a relatively high temperature component in thermal communication
with the phase transition material of the thermal conditioning system, the phase transition
material at a temperature to cool the relatively high temperature component.
[0030] A feature of the present application provides wherein the vehicle is an airborne
vehicle capable of producing lift, the internal combustion engine is capable of producing
at least one of a thrust force and a lift force.
[0031] Another feature of the present application provides wherein the work providing device
is fluid driven and structured to provide work to generate electrical power by a change
in pressure of the fluid.
[0032] Still another feature of the present application provides wherein the vehicle is
an aircraft having an external pod, the work providing device located in the external
pod.
[0033] Yet still another feature of the present application further includes a second working
fluid in thermal communication between the phase transition material and the relatively
high temperature component, the second working fluid withdrawing heat from the relatively
high temperature component and delivering heat to the phase transition material.
[0034] Still yet another feature of the present application provides wherein the vehicle
includes a second external pod having a second work providing device.
[0035] A further feature of the present application provides wherein the work providing
device is a turbine, and wherein the external pod includes an opening to receive an
air, the air in fluid communication with the turbine.
[0036] A still further feature of the present application provides wherein the internal
combustion engine is a gas turbine engine, and the air is a bleed air from the gas
turbine engine.
[0037] Another aspect of the present application provides an apparatus comprising an aircraft
having one or more propulsion engines and an external pod and including a turbine
apart from the one or more propulsion engines, the turbine in power communication
with an electrical generator and a heat exchange system that includes a phase change
heat exchanger, the aircraft further including an implement in thermal communication
with the heat exchange system.
[0038] A feature of the present application provides wherein the implement is an electrically
driven implement.
[0039] Another feature of the present application provides wherein the implement is powered
by the electrical generator and takes the form of a directed energy device.
[0040] Still another feature of the present application provides wherein the external pod
includes an opening for receiving a gas in fluid communication with the turbine.
[0041] Yet still another feature of the present application provides wherein the turbine
is located downstream of a combustor, the heat exchange system includes a first working
fluid in thermal communication with the phase change heat exchanger.
[0042] Still yet another feature of the present application further includes a pump powered
by the turbine, the pump circulating a second working fluid in thermal communication
with the implement and the phase change heat exchanger, the first working fluid part
of a vapor compression refrigeration system.
[0043] A further feature of the present application provides wherein the external pod includes
coolant supply and coolant return lines as well as an electrical conduit in communication
with the implement.
[0044] A still further feature of the present application provides wherein the heat exchange
system includes a vapor compression refrigeration system having a working fluid in
communication with the phase change heat exchanger.
[0045] Yet another aspect of the present application provides a method comprising combusting
a fuel in an internal combustion engine to provide motive force for a vehicle, operating
a work providing device to provide power to an electrically driven device aboard the
vehicle, the work providing device separate from the internal combustion engine, elevating
a temperature of the electrically driven device, cooling the electrically driven device,
the cooling including: circulating a working fluid from work provided by the work
providing device, and exchanging heat between the working fluid and a phase transition
material.
[0046] A feature of the present application further includes turning an internal combustion
engine turbine downstream of the combusting and wherein the work providing device
includes a rotatable turbine, the work providing device located in an external compartment
of the vehicle.
[0047] Another feature of the present application provides wherein the internal combustion
engine is a turbine and the vehicle is an aircraft, wherein the work providing device
is located in an external pod of the aircraft, and which further includes producing
a directed electromagnetic beam from the electrically driven device.
[0048] Still another feature of the present application provides wherein the circulating
includes expanding the working fluid to reduce the temperature thereof and condensing
the working fluid by rejecting heat from the working fluid to a relatively low temperature
sink, the circulating provided by a compressor.
[0049] Yet still another feature of the present application provides wherein the exchanging
includes reducing the temperature of the phase transition material to cause a change
in phase, which further includes halting operating of a directed energy weapon.
[0050] Still yet another feature of the present application further includes circulating
a second working fluid, the working fluid receiving heat from the phase transition
material, the phase transition material receiving heat from the second working fluid,
and the second working fluid receiving heat from the electrically driven device.
[0051] While the invention has been illustrated and described in detail in the drawings
and foregoing description, the same is to be considered as illustrative and not restrictive
in character, it being understood that only the preferred embodiments have been shown
and described and that all changes and modifications that come within the spirit of
the inventions are desired to be protected. It should be understood that while the
use of words such as preferable, preferably, preferred or more preferred utilized
in the description above indicate that the feature so described may be more desirable,
it nonetheless may not be necessary and embodiments lacking the same may be contemplated
as within the scope of the invention, the scope being defined by the claims that follow.
In reading the claims, it is intended that when words such as "a," "an," "at least
one," or "at least one portion" are used there is no intention to limit the claim
to only one item unless specifically stated to the contrary in the claim. When the
language "at least a portion" and/or "a portion" is used the item can include a portion
and/or the entire item unless specifically stated to the contrary.